Join Tek-Tips Forums! Join Us! By joining you are opting in to receive e-mail. Promoting, selling, recruiting, coursework and thesis posting is forbidden. Students Click Here. Only traffic recordings "looking backwards" Would you have a command for this? It would be very helpful. What do you want to measure? CO lines, Groups, Extension etc. There are different commands to initiate the measurements.
Traffic through the MSC over a certain period. Please let me know of the commands you are familiar with. Traffic recording on a Route CO line. HH hours. TT minutes. Operator measurement are "heavy" to understand, but very detailed and OK to get knowledge about. I also need the script to activate node after loading TN and rn script. You Spot-on! Login to download the software 17A but the page indicates "not found", would be so kind to re-upload this software please.
Another query, do you know how to configure GSM within baseband? Thank you very much for your information. Reply Adeniran September 21, at AM Can someone share with me how to configure external alarms on Ericsson baseband? Comment as: Select profile Theme images by 5ugarless. Powered by Blogger. Related Papers. Baseband Description x By erfan pouryan. Download pdf. Log in with Facebook Log in with Google. Remember me on this computer.
If the database cannot be found then you will be prompted to select a valid Winfoil V2. If a valid database is selected this setting will be updated. Printing Printer calibration may be necessary due to the age of the printer or some printer driver inaccuracy. Winfoil V2. Correction factors for rib and airfoil printing. These are normally set to 1. To increase the length of a rib if the printed output is too short, divide the measured length by the required length.
Use this value for the horizontal correction factor. To decrease the length of a rib, divide the measured length by the required length. Similarly for the vertical size enter the appropriate correction factor if incorrect.
Before changing the correction factors you should do a Test Print. Select the measurement units either Inches or Millimetres then click on the Test Print button. This action will cause a special test page to be printed. This page has a horizontal line and a vertical line. If Inches was the selected measurement units then each line will marked by one inch intervals. If Millimetres was selected then each line will be marked by 10 millimetre intervals.
You will need to measure these to ensure Ccnjiurcticn Winoil version 2. If not then enter the appropriate correction factor in the Preferences screen and reprint. Repeat this process until it is correct. Example; Examining the Vertical Line in the Test Print we find that; 1 Interval 10 millimetres is actually 8 millimetres. Therefore we need to correct the printing in the vertical axis as it is 2 millimetres short.
Click on the OK button once set. This value is used to format the numbers produced by the DXF export. The default is 4. The DOT line type is used to plot the airfoil or rib datum line. If this option is unchecked then a continuous line will be used for the datum. There are a number of Windows CAD programs on the market which do not support international number formats. Winfoil exports numeric data in a format according to the Regional Settings for the PC on which it is run. You may need to check this option if the CAD program you are using to import the DXF file does not support International number formatting.
Tools Additional programs which can be run from the Tools menu. See the Tools Tab for more detail. Export This setting is used to specify the template Excel spreadsheet file used to export performance data from Winfoil. Winfoil establishes a DDE connection with Excel to export the data to the spreadsheet.
You must have Excel installed on your computer for this function to work. If Excel cannot be found an error message will be displayed. The sample excel spreadsheet may be customised to your liking if required. To accept the changes made To accept the changes made To accept the changes made To accept the changes made Click on the OK button.
To change printers, select a printer and click on the OK button. You can then change any options as required. To obtain help on the available options click on the HELP button. This allows for more flexibility and customization without changing the actual program code.
This functionality enables users to add new aircraft configurations, design components such as fuselage formers, drag breakdown items for drag and performance analysis and drag coefficients for selected design components.
An example of a configuration is Monoplane. The configuration is used by Winfoil to create drag breakdown items for use in performance calculations. You can only modify an existing grouping. If new design components are added these must be added to the appropriate group. This parameter type is used in the Design List tabs to enable the correct style of tabs. Wing, Fuselage Former, Horizontal Tail. You cannot delete a design component once it has been created. If a new component is created then it must be entered into the appropriate component group above.
You can only create or modify drag items. Each drag item can be linked to a design component. When the drag item is modified in the Drag Breakdown tab and there is a link to a design component, then if this component has already been created in the DesignCAD tab its drag properties will automatically be retrieved. If the component has not been designed then depending on the type of item a special screen will be displayed to select a drag coefficient.
Some items will not have a link to a design component. An example of such an item is a control horn. A control horn is not designed in Winfoil. Therefore the drag coefficient for such an item must be entered with the parameter. Each Ccnjiurcticn Winoil version 2. You may modify this data if required. The data is provided in the form of a length top diameter ratio and the corresponding drag coefficient. You cannot modify these entries. You may modify this parameter type.
You cannot modify these. The top section of the screen displays the parameter type name and description. Two buttons are provided in this section. Search 8utton Search 8utton Search 8utton Search 8utton This button is used to search for parameter types.
The VCR style buttons are used to scroll through the parameters. The buttons on the lower half of the screen are used to maintain entries for each parameter. The buttons are: New 8utton New 8utton New 8utton New 8utton This button is used to create a new entry for a parameter. Parameters can also be edited by double clicking on the entry.
These buttons are enabled or disabled depending on the parameter. Some parameters can be modified or appended to whilst others can not be edited at all. Data 8ackup Data 8ackup Data 8ackup Data 8ackup To protect and preserve your data, regular data backups must be performed. Data is stored in a Microsoft Access database file. MDB from your backup floppy disk or another hard disk. These can be downloaded from any Bulletin Board Service or from the Internet.
User lnterjcce Winoil version 2. This feature is disabled in the unregistered version of Winfoil. MDI applications contain multiple screens within one container screen.
This allows you to display multiple screens at the same time with each screen displayed in its own window. You may also tile the screens by selecting the Tile option from the Window menu. By selecting the Cascade menu option from the Window Menu, you can view the three screens as overlapping screens.
To access these, right click and select the appropriate menu item. This feature reduces the need to move the mouse pointer to the menu or Toolbar to select a particular program function.
Menu short cut keys have also been introduced. Cut Cut Cut Cut This command allows data to be cut from a selected data field on a screen to the Windows Clipboard for pasting into another field within Winfoil or to any other Windows application. This data can then be pasted back into a field within Winfoil or to another Windows Application.
Paste Paste Paste Paste This command allows text that has been placed in the Windows Clipboard to be pasted in any selected data field within Winfoil. Text may be placed into the clipboard from Winfoil or from any other Windows application.
Only text may be pasted into Winfoil. Winoil version 2. About About About About This command displays Copyright information and details on the Software products used to create this program. This screen has been enhanced to also show the mode of operation, memory available and free system resources. This screen now allows you to connect to the Winfoil Web Site.
On the left is a pane containing a list of all airfoils, lift coefficients, drag coefficients, thickness to chord ratios, maximum camber and maximum camber location. This screen is resizable and the left pane may be resized individually by clicking and dragging on the black vertical border just like Explorer in Windows Winfoil stores the pane size so the next time the screen is opened, the pane is restored to its original size and position. Winfoil will plot the section of a selected airfoil in the box provided.
Any comments about the airfoil will appear in the box below the plot. If Lift and Drag data is available for the selected airfoil, the following icon appears to the right of the airfoil name. The higher the value the greater the amount of lift that the airfoil generates. A short take off and landing aircraft requires a high lift airfoil therefore one would select an airfoil with a very high CL Coefficient of lift.
CD MIN is the minimum drag coefficient. An airfoil with a low drag coefficient and good lift coefficient will provide excellent gliding performance. A high drag airfoil will provide poor glide performance, acceleration and climb performance. CM MAX is the maximum pitching moment coefficient.
A positive value means that the airfoil will pitch up, a negative value means that the airfoil will pitch down. Tailless aircraft require a positive pitching moment for pitch stability. Therefore one would choose an airfoil with a positive pitching moment. This can also be achieved with an airfoil with zero pitching moment e. The larger the pitching coefficient the greater the force required to balance the aircraft. To minimise tail areas for minimal drag on conventional wing and tail designs one would select an airfoil with a low pitching moment.
Thickness is the maximum thickness of the airfoil, i. Camber is the maximum camber of the airfoil expressed as a percentage of the chord. Typically airfoil performance improves with higher Reynolds Numbers therefore it is more important to have details on performance at low Reynolds Numbers.
This screen can also be accessed quickly from the Toolbar by clicking on the button or pressing the Ctrl key and the A key at the same time. Click on the Airfoil tab. Click on the NEW button. You will then be prompted to either add an airfoil manually or to select the NACA airfoil wizard. If you are creating a new airfoil manually you must enter the name of the airfoil.
If you enter the name of an airfoil which already exists an error message will be displayed and Winfoil will prevent you creating an airfoil with the same name. If you selected the manual option you have two ways of creating the new airfoil. The Lift, Drag and Pitching moment coefficients for the airfoils in the Winfoil database are for the lowest Reynolds Number and standard roughness conditions.
They are to be used only as a guide to selection of a suitable airfoil. Performance of model aircraft will, of course, vary due to the low Reynolds Number at which model aircraft fly. The screen can be accessed from the Toolbar by clicking on the button. Click on the Coordinates Tab. This tab is provided to allow airfoil coordinates to be entered, deleted or changed. Three different formats are provided: 1. NACA 2. Eppler 3. Eppler To change format you must click on the appropriate radio button at the bottom of the tab.
To add new coordinates click on the ADD button. All coordinates are expressed as a percentage of chord. Data is entered in pairs, i. The X axis is the axis running lengthways along the chord of the airfoil. The Y axis is the axis running perpendicular to the X axis. X coordinate pairs do not have to match.
Xupper: Upper surface x coordinate distance from the leading edge Yupper: Upper surface y coordinate height above datum line Xlower: Lower surface x coordinate distance from the leading edge Ylower: Lower surface y coordinate height above the datum line Note: negative values lie below the datum line.
When you select this button, a dialogue box will prompt you that you are about to delete an airfoil. Be careful when you use this button, deleted airfoils cannot be recovered!
Three additional boxes are provided to enter: Cl Max. To update, amend or clear these values, type the value into the box and select another airfoil from the list of airfoils. You must enter data in pairs, i. The x coordinate pairs do not have to match. All coordinates are expressed as a percentage of the chord. The X axis is the axis running lengthways along the airfoil chord. The Y axis is the axis perpendicular to the X axis.
Xupper: Upper surface x coordinate distance from the leading edge Yupper: Upper surface y coordinate height above the datum line Xlower: Lower surface x coordinate distance from the leading edge Ylower: Lower surface y coordinate height above the datum line Note: negative values lie below the datum line. To change coordinates, select the coordinates and click on the CHANGE button or double click on the selected coordinate row.
For all reynolds Numbers 2. For the lowest Reynolds Number 3. For one of the listed Reynolds Numbers for the selected airfoil. These values can then be used later for searching for an airfoil for a new design. How to use this feature; 1. Select one of the criteria for the lookup. Click on the OK button to process or click on the Cancel button to exit. Multiple lines of comment may be added up to a maximum of characters.
The function of the button will be shown on the status bar at the bottom left hand side of the screen. If this option is not checked, you must click on the ADD button to add the coordinates.
Data is provided for a number of Reynolds Number readings. Click on the Polar Graph Tab. In general most airfoils suffer a loss in performance with a reduction in Reynolds Numbers. If you choose an airfoil which performs well at a low Reynolds Number, the same airfoil will typically perform much better at higher Reynolds Numbers. The lower the drag coefficient Cd , the lower the profile drag for a given wing or tail area. Low drag is required for Pylon and Sailplane designs. Funfly designs rely on high drag sections for even speed through manoeuvres.
Please note that this data is for infinite aspect ratios. The actual lift and drag coefficients for real designs will be lower and higher depending on the Aspect Ratio of the wing or tail. It increases structural loading good for gliding and reduces roll rate high inertia.
It reduces structural loading good for aerobatics and improves roll rate. The higher the Aspect Ratio, the closer the performance of the wing or tail will match the test data. There is one button on this screen, the Save button. Save 8utton Save 8utton Save 8utton Save 8utton This button saves the current graph as a Windows bitmap graphic file.
The graphic file can subsequently be viewed or pasted into a document. To access the Lift Graph tab: 1he Airjcil list Winoil version 2. Click on the Lift Graph Tab. The higher the Aspect Ratio the closer the performance of the wing or tail will match the test data. To access the Lift Drag Data Maintenance tab: 1. Enter the Reynolds Number and click on the OK button.
Add lift and drag coefficient data by clicking on the ADD button on the lower right section of this screen. Enter the data as required. This will cause data to be updated automatically after you tab off the drag coefficient text box.
Tip Data is always entered for a Reynolds Number set. To add a new set you must add the Reynolds Number first, followed by the lift, drag and angle of attack data. To view the data for a different Reynolds Number, click on the Reynolds Number Grid at the upper left of the screen.
This screen consists of a scrollable region Airfoil Window on which the airfoil is plotted, status bar and Toolbar. The status bar is used to inform the user of the functions of each button on the Toolbar and to show the date and time. The x axis is the axis running along the chord of the airfoil. The y axis is the axis perpendicular to the x axis with its origin at the leading edge of the airfoil. A template facility is provided to accurately set the position of the coordinates for the leading edge.
If new coordinates have been entered, you will be asked whether you want to accept the changes. You can discard changes if you wish. The Leading Edge Radius Template is used as a guide to the positioning of coordinates to ensure that an accurate leading edge radius is obtained.
Redraw airfoil section Show airfoil coordinate points. The red points indicate existing data. The blue points indicate new airfoil coordinates added whilst in this screen. Clicking the button toggles this feature on and off. This button increases the size of the airfoil. This button reduces the size of the airfoil.
This button is used to select the Leading Edge Radius Template feature. When this button is clicked, any movement of the mouse within the airfoil window will cause a circle to move about over the plot of the airfoil. The position of this template can be set with a click on the left mouse button. Coordinates can then be set using the mouse. This is expressed as a percentage of the thickness of the airfoil. This button is used to toggle the Leading Edge Radius Template on and off.
This button is used to modify the camber of an airfoil. This button is used to mirror one of the surfaces of an airfoil. This button is used to select a coordinate pair.
Click on the button then move the mouse pointer over the Airfoil Window. Click in the Airfoil Window near or on a coordinate pair with the left mouse button. Winfoil will search for the nearest coordinate pair and highlight the pair with a grey rectangle. This button is used to add new coordinates.
If the left mouse button is pushed with the mouse pointer in the Airfoil Window, a coordinate will be placed at that position. Clicking on the right mouse button will cancel the operation. All coordinates are entered as a pair, i. Once the top coordinate is set, the lower coordinate x position will be restrained by the upper coordinate x position. However you are free to vary the y position of the lower coordinate. This button is used to discard all changes made.
All new coordinates are deleted. If a coordinate pair is selected framed with a grey rectangle , this button deletes the coordinate pair. This button is used to accept the new coordinates and redraw the airfoil. This button opens the Overlay Airfoil screen to select an airfoil to overlay over the selected airfoil. To select a particular coordinate pair, click on the spin buttons. The left spin button searches to the left towards the leading edge of the airfoil and the right spin button searches towards the right of the airfoil trailing edge.
Increase the size of the airfoil by clicking on the button. Scroll the airfoil so that the leading edge is in the centre of the airfoil window. The size of the airfoil should be such that accurate placing of coordinates can be made.
If the airfoil is too large, click on the button to reduce the size. If you wish to modify the leading edge radius proceed to Step 2, otherwise, go to Step 3. Select a leading edge radius. Click on the button. Move the mouse pointer within the airfoil window and position the Leading Edge Radius Template appropriately. Add coordinates in the Airfoil window, one pair at a time, by moving the mouse pointer to the required position e.
Click on the left mouse button. Move the mouse pointer down, e. The new coordinate pair will be shown as 2 blue spheres. Continue to add coordinate pairs, starting with the top coordinate, then the bottom, repeating the process as often as necessary.
Click on the button to save the new coordinates and to redraw the airfoil. To stop adding coordinates because you have made a mistake, simply right click while in the Airfoil Window or click the button to discard changes. To modify a coordinate pair, click on the button then move the mouse pointer over the Airfoil Window.
Winfoil will search for the nearest coordinate pair and will when found, highlight the pair with a grey rectangle. To move one of the coordinates of the pair you may only shift the coordinate up or down , click on the grey Handle and drag it up or down to the desired position and the change is automatically saved.
To undo a change, click on the button. To delete a coordinate pair, click on the button then move the mouse pointer over the Airfoil Window. Click in the Airfoil Window on or near a coordinate pair. Winfoil will search for the nearest coordinate pair and when found, highlights the pair with a grey rectangle. To delete the coordinate pair click on the button. This screen consists of a scrollable region airfoil window on which the airfoil is plotted, status bar and Toolbar.
The buttons on the Toolbar are used to enter new coordinates, delete coordinates, increase and decrease the size of the airfoil plot and to toggle on and off the visibility of the data coordinates. Click with the left mouse button in the Airfoil Window on or near a coordinate pair. To move one of the coordinates of a pair you may only shift the coordinate up or down click on the grey HANDLE and drag it up or down to the desired position.
This automatically saves the change. To undo the change, click on the button. Winfoil searches for the nearest coordinate pair and, when found, highlights the pair with a grey rectangle. Click on the button to delete the coordinate pair.
Steps Steps Steps Steps 1. Select an airfoil to copy from the drop down list by clicking on the down arrow or type the first character of the name of the airfoil you wish to copy. Click the check boxes to select data to be copied. All are selected by default. Enter the name of the new airfoil If you enter the name of an existing airfoil in the New Airfoil Name box then you will be prompted to confirm that you wish to overwrite the existing airfoil.
Modifying existing airfoils is not recommended. In most cases, without thorough knowledge of aerodynamics and wind tunnel testing, modifications will reduce performance and produce poor flight and stability characteristics. To change from viewing lift data to drag data simply click on the tab at the top of the screen. The thick black line indicates that the screen can be altered by the user to size the portion of the screen that contains the graph. To increase the area for the graph, move the mouse pointer over the black line and drag the line up or down.
The mouse pointer will change as you move over this line. The graph size is proportional to the window size. It will automatically change size as the screen changes in size. The data on this screen is supplied as two separate graphs. The first is the lift coefficient Cl vs angle of attack Alpha in degrees. The second is lift coefficient vs. As model aircraft typically fly at low Reynolds Numbers i. The higher the lift coefficient Cl the greater the lift produced by an airfoil and the lower the stall speed for a given wing area.
Note that this data is for infinite aspect ratios. Actual lift and drag coefficients will be lower and higher depending on the Aspect Ratio of the wing or tail.
There are three buttons on thIs screen. Save button Save button Save button Save button This button saves the current graph as a Windows bitmap graphic file. The graphic file can be viewed at a later date or pasted into a document.
Tip A good way of viewing and comparing airfoils is to open this screen for four different airfoils. Click on the Window Tile Vertical menu to easily view the data for all four airfoils. To add data To add data To add data To add data 1. Type the new name and click on the OK button to change the name. You cannot change the name to a name which is currently being used by another airfoil.
Camber cannot be altered for symmetrical airfoils as these have no camber. Camber is expressed as a percentage of the chord of an airfoil. The point of maximum camber can not be altered by this screen. Camber is the maximum deviation from a datum line and a line passing through the leading and trailing edge of an airfoil. The datum line being a line running from the leading edge to the trailing edge and located midway between the upper and lower surface of the airfoil.
A symmetrical airfoil has no camber. Thickness is expressed as a percentage of the chord of an airfoil. The location of the maximum thickness point is not altered by this screen. Thickness is the maximum top-to-bottom depth of an airfoil section. It is expressed as a percentage of the airfoil chord.
The thickness of an airfoil affects the profile drag of an airfoil. The greater the thickness, the higher the profile drag. Profile drag is drag not produced by lift from an airfoil.
High thickness ratios tend to cause stalling at lower lift coefficients. A forward location of maximum thickness tends to cause higher drag than an aft location. Click on the OK button to make the change. Airfoil coordinates are entered in this screen using the mouse and a leading edge template.
The leading edge template is positioned on the screen with the mouse as a guide to ensure an accurate leading edge radius. The curve fitting routine used by Winfoil requires that a reasonable number of coordinates are entered to approximate the curvature of the airfoil. If insufficient coordinates are entered, the leading edge curvature will not match correctly. To search on an airfoil name, click in the name column with the mouse and type the name of the airfoil to search for in the yellow text box.
As you type the list of airfoils reduces until a perfect match is found or not found. Similarly, for the other airfoil attributes, you can initiate a search on any selected column by clicking on the column with the mouse. The other powerful feature of this search screen is the ability to sort in any order for a selected column. For example: Suppose you wish to search for an airfoil with the highest maximum lift coefficient. Click on the Clmax column with the mouse.
Then click on the Descending option for the sort order. All airfoils will be sorted on Clmax in descending order. Selecting the first airfoil will give you the airfoil with the maximum lift coefficient.
After selecting an airfoil, click on the OK button to return to the Airfoil List. Double clicking on a selection automatically activates the OK button. The function of the button will be shown on the status bar at the left side of the bottom of the screen.
These chord lengths are stored in a database table within Winfoil. Increasing this value increases plot time. If this option is not checked, Winfoil automatically prints airfoils one after the other and only starts printing on a new page when necessary. Airfoil size is limited to screen size. If multiple airfoils are printed, only those that fit on one screen will be captured.
Separate files are produced for each airfoil or rib. When setting up the drawing size, you must select corresponding measurement units in the CAD program before importing the DXF file, e. You may cancel the print job at any time by clicking on the CANCEL button or if this dialog box has disappeared by deleting the print job in Print Manager. Winfoil can now cater for airfoils longer than the paper size. It will automatically tile the printed airfoil over multiple pages. This screen is an explorer style screen.
On the left is a pane containing a tree directory list of all designs stored in the Winfoil database. You can now create specifications and fuselage components.
Specifications, fuselage components, wings and tail planes are grouped together by name design items. If the airfoil is not in Winfoil then obtain and enter Airfoil coordinates.
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